Turbojet engine nacelle with a cascade thrust reverser comprising a flap control sector

Abstract

A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.

What is claimed is: 
     
       1. An engine nacelle of a bypass turbojet engine type disposed along a main axis, the engine nacelle comprising:
 a thrust reverser system having at least one movable cowl movable axially between a direct jet front position and a reverse jet rear position which tilts a plurality of pivoting flaps while at least partially closing an annular flow path, and which opens lateral openings of the annular flow path upstream of the plurality of pivoting flaps, equipped with thrust reverser cascades returning a cold air flow towards outside forwards, wherein each movable cowl includes:
 a control sector sliding in a transverse plane relative to the main axis; 
 a return device connecting a fixed portion of the engine nacelle to the control sector to slide the control sector to a reversal position when the at least one movable cowl is recoiled; and 
 a plurality of flap tie-rods connecting the control sector to the plurality of pivoting flaps disposed in front of the at least one movable cowl and movable by the control sector, the plurality of flap tie-rods tilting the plurality of pivoting flaps by closing the annular flow path upon movement by the control sector when sliding the control sector towards the reversal position, 
 
 wherein each flap of the plurality of flaps includes a safety hook fixed to the control sector, the safety hook securing the reversal position by applying on the flap in the direct jet position, a force parallel to a movement of the flap. 
 
     
     
       2. The engine nacelle according to  claim 1 , wherein each flap tie-rod includes a play take-up system comprising at least two axial portions sliding relative to each other, equipped with an intermediate spring. 
     
     
       3. The engine nacelle according to  claim 1 , wherein the control sector includes guides fixed to the at least one movable cowl, allowing a movement of the control sector according to a circumferential direction. 
     
     
       4. The engine nacelle according to  claim 1 , wherein each control sector includes the return device at each end of the control sector. 
     
     
       5. The engine nacelle according to  claim 1 , wherein the return device comprises a return plate fixed to the at least one movable cowl by a cowl pivot, the return plate being connected to the fixed portion of the nacelle by a primary tie-rod and to the control sector by a secondary tie-rod. 
     
     
       6. The engine nacelle according to any  claim 1 , wherein the return device comprises a rack linked to the fixed portion and disposed parallel to the main axis, and a pinion engaged on the rack, linked to the at least one movable cowl. 
     
     
       7. The engine nacelle according to  claim 6 , wherein the return device includes a secondary tie-rod connecting the pinion to the control sector. 
     
     
       8. The engine nacelle according to  claim 6 , wherein the pinion drives a cam receiving a connecting pin connected to the control sector. 
     
     
       9. The engine nacelle according to  claim 6 , wherein the pinion drives a pinion at an angle connected to the control sector by a screw-nut system. 
     
     
       10. The engine nacelle according to  claim 1 , wherein the return device comprises a cam receiving a connecting pin, one of the cam or the connecting pin axially sliding during a recoil movement of the at least one movable cowl, and the other of the connecting pin or the cam being linked to the control sector. 
     
     
       11. The engine nacelle according to  claim 1 , wherein the return device comprises a cable fixed to the control sector in a transverse direction, passing from each side of the control sector by a pulley linked to the at least one movable cowl taking an axial direction rearwards on one side and forwards on the other side, to then be fixed to the fixed portion. 
     
     
       12. The engine nacelle according to  claim 1 , wherein the return device is controlled directly by movement of the movable cowl. 
     
     
       13. The engine nacelle according to  claim 1 , wherein the control sector further includes an elongated and curved bar held inside the movable cowl in the transverse plane by one or more guides. 
     
     
       14. The engine nacelle according to  claim 1 , wherein the return device includes a return plate spaced apart from the fixed portion of the engine nacelle and the control sector and pivotable relative to the fixed portion and the control sector, and wherein pivoting of the return plate relative to the fixed portion of the engine nacelle causes the return plate to pivot relative to the control sector and changes a distance of the return plate from the fixed portion of the engine nacelle and from the control sector. 
     
     
       15. An engine nacelle of a bypass turbojet engine type disposed along a main axis, the engine nacelle comprising:
 a thrust reverser system having at least one movable cowl movable axially between a direct jet front position and a reverse jet rear position which tilts a plurality of pivoting flaps while at least partially closing an annular flow path, and which opens lateral openings of the annular flow path upstream of the plurality of pivoting flaps, equipped with thrust reverser cascades returning a cold air flow towards outside forwards, wherein each movable cowl includes:
 a control sector sliding in a transverse plane relative to the main axis; 
 a return device connecting a fixed portion of the engine nacelle to the control sector to slide the control sector to a reversal position when the at least one movable cowl is recoiled; and 
 a plurality of flap tie-rods connecting the control sector to the plurality of pivoting flaps disposed in front of the at least one movable cowl and movable by the control sector, the plurality of flap tie-rods tilting the plurality of pivoting flaps by closing the annular flow path upon movement by the control sector when sliding the control sector towards the reversal position, 
 
 wherein the return device comprises a return plate fixed to the at least one movable cowl by a cowl pivot, the return plate being connected to the fixed portion of the nacelle by a primary tie-rod and to the control sector by a secondary tie-rod. 
 
     
     
       16. The engine nacelle according to  claim 15 , wherein each flap tie-rod includes a play take-up system comprising at least two axial portions sliding relative to each other, equipped with an intermediate spring. 
     
     
       17. The engine nacelle according to  claim 15 , wherein the control sector includes guides fixed to the at least one movable cowl, allowing a movement of the control sector according to a circumferential direction. 
     
     
       18. The engine nacelle according to  claim 15 , wherein each control sector includes the return device at each end of the control sector. 
     
     
       19. The engine nacelle according to any  claim 15 , wherein the return device is controlled directly by movement of the movable cowl. 
     
     
       20. The engine nacelle according to  claim 15 , wherein the control sector further includes an elongated and curved bar held inside the movable cowl in the transverse plane by one or more guides. 
     
     
       21. The engine nacelle according to  claim 15 , wherein the return plate is spaced apart from the fixed portion of the engine nacelle and the control sector and pivotable relative to the fixed portion and the control sector, and wherein pivoting of the return plate relative to the fixed portion of the engine nacelle causes the return plate to pivot relative to the control sector and changes a distance of the return plate from the fixed portion of the engine nacelle and from the control sector. 
     
     
       22. An engine nacelle of a bypass turbojet engine type disposed along a main axis, the engine nacelle comprising:
 a thrust reverser system having at least one movable cowl movable axially between a direct jet front position and a reverse jet rear position which tilts a plurality of pivoting flaps while at least partially closing an annular flow path, and which opens lateral openings of the annular flow path upstream of the plurality of pivoting flaps, equipped with thrust reverser cascades returning a cold air flow towards outside forwards, wherein each movable cowl includes:
 a control sector sliding in a transverse plane relative to the main axis; 
 a return device connecting a fixed portion of the engine nacelle to the control sector to slide the control sector to a reversal position when the at least one movable cowl is recoiled; and 
 a plurality of flap tie-rods connecting the control sector to the plurality of pivoting flaps disposed in front of the at least one movable cowl and movable by the control sector, the plurality of flap tie-rods tilting the plurality of pivoting flaps by closing the annular flow path upon movement by the control sector when sliding the control sector towards the reversal position, 
 
 wherein the return device includes a return plate spaced apart from the fixed portion of the engine nacelle and the control sector and pivotable relative to the fixed portion and the control sector, and wherein pivoting of the return plate relative to the fixed portion of the engine nacelle causes the return plate to pivot relative to the control sector and changes a distance of the return plate from the fixed portion of the engine nacelle and from the control sector. 
 
     
     
       23. The engine nacelle according to  claim 22 , wherein each flap tie-rod includes a play take-up system comprising at least two axial portions sliding relative to each other, equipped with an intermediate spring. 
     
     
       24. The engine nacelle according to  claim 22 , wherein the control sector includes guides fixed to the at least one movable cowl, allowing a movement of the control sector according to a circumferential direction. 
     
     
       25. The engine nacelle according to  claim 22 , wherein each control sector includes the return device at each end of the control sector. 
     
     
       26. The engine nacelle according to  claim 22 , wherein the return device is controlled directly by movement of the movable cowl. 
     
     
       27. The engine nacelle according to  claim 22 , wherein the control sector further includes an elongated and curved bar held inside the movable cowl in the transverse plane by one or more guides.